Angle of Attack Estimation Using an Inertial Reference Platform. Meeting Paper AIAA-1988-4351, Research Engineering, NASA Dryden Flight Research Center

Zeis Jr., Capt Joseph E. and Lambert, Heather H. and Calico, Robert A. and Gleason, Maj Daniel (1988) Angle of Attack Estimation Using an Inertial Reference Platform. Meeting Paper AIAA-1988-4351, Research Engineering, NASA Dryden Flight Research Center.

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Abstract

This paper presents the mathematical development and flight test results of an angle of attack estimation system based on inertial navigation system inputs. The estimator uses these inputs to determine the coefficient of lift required at any instant inflight. Angle of attack is then modeled through a regression analysis based on coefficient of lift, altitude and Mach. Overall correlation of the estimator as tested was generally within 0.5 degrees through 17 degrees angle of attack on an F-15A aircraft. A robustness analysis indicates that the system can be used adequately in maneuvering flight.

EPrint Type:	Other
Keywords:	F-15A aircraft
Subjects:	Aircraft/Project: F-15
ID Code:	1476
Deposited On:	21 March 2007
Additional Information:	11 pages. AIAA Atmospheric Flight Mechanics Conference, Minneapolis, Minnesota, August 15-17, 1988.